为实现再入飞行时间可控,扩展现有再入飞行器的应用场景,提高对时间敏感目标的打击能力,以双参数牛顿迭代法为基础,提出一种改进的阻力加速度剖面设计方法,通过设置双参数校正点,能够同时对轨迹长度与总飞行时间进行设计。在给定的轨迹长度与总飞行时间约束下,该方法能够快速完成参考阻力加速度剖面的迭代,生成满足各项约束的参考轨迹。通过仿真分析获得了再入总飞行时间的调节规律,为多再入飞行器的协同攻击问题提供依据。

In order to control the reentry flight time, expand the application scenarios of existing reentry vehicles and improve the strike capability against time sensitive targets, this paper proposes an improved drag acceleration profile which could determine the trajectory length and the total flight time simultaneously based on the two-parameter Newton iterative method. The iteration of reference drag acceleration profile can be done quickly and the reference trajectory with different constraints can be generated using the proposed method. Finally, the regulation law of the total reentry flight time is obtained by simulation analysis, which provides a basis for the cooperative problem of multiple reentry vehicles.